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  • 1
    Publication Date: 2013-08-31
    Description: The availability of megawatt laser systems in the next century will make laser launch systems from ground to orbit feasible and useful. Systems studies indicate launch capabilities of 1 ton payload per gigawatt laser power. Recent research in ground to orbit laser propulsion has emphasized laser supported detonation wave thrusters driven by repetitively pulsed infrared lasers. In this propulsion concept each laser repetition cycle consists of two pulses. A lower energy first pulse is used to vaporize a small amount of solid propellant and then after a brief expansion period, a second and higher energy laser pulse is used to drive a detonation wave through the expanded vapor. The results are reported of numerical studies comparing the detonation wave properties of various candidate propellants, and the simulation of thruster performance under realistic conditions. Experimental measurements designed to test the theoretical predictions are also presented. Measurements are discussed of radiance and opacity in absorption waves, and mass loss and momentum transfer. These data are interpreted in terms of specific impulse and energy conversion efficiency.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Lewis Research Center, Vision-21: Space Travel for the Next Millennium; p 193-201
    Format: application/pdf
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  • 2
    Publication Date: 2019-06-28
    Description: The excitation mechanisms and radiance estimates over the 1 to 10 micron region for CO2(v), H2O(v), CO(v), OH(v), NO2(2B-2A) and N2(B3 pi - A3 sigma) are discussed. The infrared irradiance of the Space Station at an altitude of 460 km was estimated. The surface material was presumed to be non-carbonaceous and inert. The determined number densities of the various gases relevant to the Space Station from both ambient and outgassing sources are presented. A model for the production of and emission from the infrared active molecules was constructed that considers two classes of production processes: (1) gas phase excitation of molecules in the near Station environment by collision with ambient flux; and (2) surface processes that lead to molecular excitation. A composite spectrum of all major emitting species shows that the observed irradiance is non-uniform over the 1 to 8 micron region. The comparison of predicted irradiance with the zodiacal background indicates that the Space Station infrared background from atmosphere-induced emissions may be a problem of consequence.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Langley Research Center, A Study of Space Station Contamination Effects; p 61-69
    Format: application/pdf
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  • 3
    Publication Date: 2019-06-27
    Description: Systems analysis, design, and operating characteristics of strapdown gyroscopes for dynamic environment
    Keywords: NAVIGATION
    Type: NASA-CR-86082 , TR-101-3 , SAR-2
    Format: application/pdf
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  • 4
    Publication Date: 2019-06-27
    Description: Error analysis for single degree of freedom integrating gyro, and figure of merit relating gyro errors to orientation error of strapdown inertial reference system
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-86037 , TR-101-2
    Format: application/pdf
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  • 5
    Publication Date: 2019-07-13
    Description: Single degree of freedom integrating gyro in strapdown inertial systems, discussing error reduction
    Keywords: NAVIGATION
    Type: AIAA PAPER 68-830 , GUIDANCE, CONTROL, AND FLIGHT DYNAMICS CONFERENCE; Aug 12, 1968 - Aug 14, 1968; PASADENA, CA
    Format: text
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